CN113266473B - Method for measuring starting resistance moment of aero-engine under non-loading condition - Google Patents
Method for measuring starting resistance moment of aero-engine under non-loading condition Download PDFInfo
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- CN113266473B CN113266473B CN202110609249.2A CN202110609249A CN113266473B CN 113266473 B CN113266473 B CN 113266473B CN 202110609249 A CN202110609249 A CN 202110609249A CN 113266473 B CN113266473 B CN 113266473B
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/26—Starting; Ignition
- F02C7/268—Starting drives for the rotor, acting directly on the rotor of the gas turbine to be started
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
- F01D21/003—Arrangements for testing or measuring
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/36—Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/14—Testing gas-turbine engines or jet-propulsion engines
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- Combustion & Propulsion (AREA)
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- General Physics & Mathematics (AREA)
- Testing Of Engines (AREA)
Abstract
The application belongs to the technical field of engine tests, and particularly relates to a method for measuring starting resistance torque of an aero-engine under the condition of no loading. An air source control device drives an air turbine starter to rotate, the air turbine starter drives an engine to start, and a torque measuring device is arranged on the power transmission shaft; calibrating the air source condition of the starting process of the engine, and carrying out an engine starting test by utilizing the calibrated air source condition; within the time period from the successful starting of the engine to the completion of the starting, acquiring the residual torque of the power transmission shaft and acquiring the engine rotating speeds of a plurality of corresponding time nodes; an engine starting drag torque is determined. This application is through the measurement to the moment of resistance of a plurality of time nodes of engine starting process, can be more accurate acquire engine starting process test data, experimental easy operation is convenient for realize, can obtain real aeroengine starting moment of resistance measuring result.
Description
Technical Field
The application belongs to the technical field of engine tests, and particularly relates to a method for measuring starting resistance torque of an aero-engine under the condition of no loading.
Background
An aircraft engine is one of the most important devices of an aircraft and can provide necessary thrust for the flight of the aircraft. The aero-engine is transited from a static state to a working state, the aero-engine can be effectively started only by the aid of the driving of the starter, and the output torque of the starter needs to overcome the influence of the resistance torque of the aero-engine. Therefore, the resistance torque in the starting process of the aircraft engine has direct influence on the type selection and the starting performance of the starter. In the traditional model design process, the starting system is taken as an important assessment item and is specified in GJB 241A-2010, GJB2187A-2015 and HB 6630-92 in detail.
In the design process of the conventional starting system of the aircraft engine, the design of the relevant starting system is developed mainly by calibrating the output torque characteristic of a starter and applying a mode of combining engineering experience and tests, and the design method mainly has the following difficulties and problems in several aspects:
1. because the starting process of the aircraft engine is a complex dynamic process, the structural parameters of internal geometric components, the working environment of engine starting, the efficiency of rotor components of the engine and the like all influence the resisting moment in the starting process of the engine, and how to accurately calibrate the starting resisting moment of the engine so as to obtain the starting load characteristics of the engine, a starter and an airplane is a complex engineering problem;
2. the conventional method for starting the aircraft engine by using the gas turbine starter has the advantages that the output torque of the starter can be changed by adjusting the oil supply flow through the oil supply main pump within a certain range, the starting test needs to be carried out through the starters with different power levels in the test process, the resource consumption is high, and the test period and the cost are high;
3. the relation between the starting time of the engine and the residual torque cannot be accurately given in the starting process of the engine, the starting time has a crucial relation to the mission starting of the airplane, the starters are usually screened in the similar engine analogy mode in the previous model design process, once the starter is selected, the starting time is determined by the starter, and the relation between the starting time and the starting residual power cannot be found through forward design;
4. after the aircraft engine is used for a long time, the performance of components of the engine can be degraded, and the starting resistance moment of the engine can also be changed, particularly after the aircraft engine is repaired. Because part of components are replaced, the factory inspection after the overhaul is mainly the basic routine inspection, and the difference between the starting resistance moment of the engine after the overhaul and the original state cannot be accurately obtained by adopting the traditional measuring method;
disclosure of Invention
In order to solve the above problems, the present application provides a method for measuring starting moment of drag of an aircraft engine under an unloaded condition, which mainly comprises:
the method comprises the following steps that S1, a turbine starter is driven to rotate through an air source control device, a gear shaft of an accessory transmission device is driven to rotate by the turbine starter, and the turbine starter is connected with an engine transmission device through a power transmission shaft, so that the engine transmission device is driven to start, and a torque measuring device is arranged on the power transmission shaft;
s2, calibrating air source conditions in the starting process of the engine, and performing an engine starting test by using the calibrated air source conditions;
s3, acquiring total residual torque values of the engine at different rotating speeds from starting to finishing starting, recording the environmental pressure as p0, and recording the air source flow as Wa air, the total pressure as pt air and the total temperature as Tt air;
s4, determining starting resistance moment M of the aero-engine T ＝M General (1) -M st 。
Wherein, M st For turbo starter output torque:
wherein, C p Is a constant, eta Air (a) Efficiency of air pipe system (including control valve) (. Eta.) ATS For turbo-starter efficiency, p tATS The total pressure at the inlet of the turbine starter is eta, and the efficiency of a transmission system is eta Transmission gear 。
Preferably, in step S2, an engine start control plan and a timing are acquired, and an engine start test is performed according to the engine start control plan and the timing.
Preferably, in step S2, an engine start control plan and a timing are acquired, and an engine start test is performed according to the engine start control plan and the timing.
Preferably, in step S2, the air supply conditions for the calibration of the engine starting process include flow, temperature, pressure, air turbine starter parameters, air line and control valve parameters, and torque measuring device parameters of the calibration air supply.
Preferably, the turbo starter is an air turbo starter.
Preferably, in step S4, N M are calculated T And fitting a functional relation graph of the starting resistance torque of the engine and the rotating speed of the engine.
Preferably, M is removed before step S4 T Outlier points in the values.
Preferably, in step S4, N is 80 to 120.
The resistance torque of the engine is directly measured through tests, the output torque characteristic of the air turbine starter mainly converts the energy of air into mechanical shaft power, the measurement precision is high, oil supply and control for the air turbine starter are not needed, the exhaust gas temperature of the air turbine starter is far lower than the exhaust gas emission temperature of the gas turbine starter, the test operation is simple and convenient to achieve, and a real engine starting resistance torque result can be obtained.
According to the method and the device, the resistance moment of a plurality of time nodes in the starting process of the engine is measured, the test data of the starting process of the engine can be acquired more accurately, the test operation is simple and convenient to realize, and the real measuring result of the starting resistance moment of the aero-engine can be acquired.
Drawings
FIG. 1 is a flow chart of a method for measuring starting drag torque of an aircraft engine under an unloaded condition.
FIG. 2 is a flow chart of an aircraft engine starting drag torque measurement test under unloaded conditions.
FIG. 3 is a schematic diagram of an aviation conventional engine starting resistance moment measurement test environment under an unloaded condition.
FIG. 4 is a schematic view of an aircraft engine starting drag torque measurement test environment under an unloaded condition.
FIG. 5 is a graphical illustration of aircraft engine starting drag torque versus rotational speed under unloaded conditions.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the accompanying drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are implementations that are part of this application and not all implementations. The embodiments described below with reference to the accompanying drawings are exemplary and intended to be used for explaining the present application and should not be construed as limiting the present application. All other embodiments obtained by a person of ordinary skill in the art without any inventive work based on the embodiments in the present application are within the scope of protection of the present application. Embodiments of the present application will be described in detail below with reference to the drawings.
The invention provides a method for measuring starting resistance torque of an aircraft engine under the condition of no loading, which mainly comprises the following steps as shown in figure 1:
the method comprises the following steps that S1, a turbine starter is driven to rotate through an air source control device, a gear shaft of an accessory transmission device is driven to rotate by the turbine starter, and the turbine starter is connected with an engine transmission device through a power transmission shaft, so that the engine transmission device is driven to start, and a torque measuring device is arranged on the power transmission shaft;
s2, calibrating air source conditions in the starting process of the engine, and performing an engine starting test by using the calibrated air source conditions;
step S3, obtaining the total residual torque value M of the engine at different rotating speeds n from starting to finishing starting General assembly Recording the ambient pressure p 0 Air supply flow W a air Total pressure p t air Total temperature T t air ；
S4, determining starting resistance moment M of the aero-engine T ＝M General (1) -M st 。
Wherein, M st For turbo starter output torque:
wherein, C p Constant, air line system (including control valve)) Efficiency is eta Air (a) Efficiency eta of turbo-starter ATS Total pressure at the entrance of the turbo starter is p tATS The transmission system efficiency is eta Transmission gear 。
In some alternative embodiments, in step S2, an engine start control plan and timing are obtained, and an engine start test is performed according to the engine start control plan and timing.
In some alternative embodiments, the air supply conditions for the calibration engine starting process in step S2 include flow, temperature, pressure, air turbine starter parameters, air line and control valve parameters, and torque measuring device parameters of the calibration air supply.
In some alternative embodiments, the turbo starter is an air turbo starter.
In some alternative embodiments, in step S4, N M are calculated T And fitting a functional relation graph of the starting resistance moment of the aircraft engine and the rotating speed of the engine.
In some alternative embodiments, M is removed prior to step S4 T Outlier points in the values.
In some optional embodiments, in step S4, N is 80 to 120.
The following examples are given.
The first step is as follows: starting a certain type of engine under the condition of a fixed air source for 36s, and recording the total intake pressure of the engine under the condition of the air source as p t air =450kPa, ambient pressure p t0 =101kpa, pressure drop ratio pi C =4.455, total inlet air temperature is T t air =483K, inlet flow Wa t air =1.1kg/s, then intake air source power psotal =185.51kw;
the second step: obtaining the total residual torque M of the engine when the rotating speed of the engine is 3000rpm through a torque sensor General assembly ＝M st +M T ＝196.6N.m；
The third step: according to
η Air (a) For fastening air pipe systemsWith loss, calibrated on the bench, of 0.9, eta ATS The efficiency at 3000rpm of the corresponding engine speed is found to be 0.63 by looking up the table; eta Transmission gear The efficiency of the air turbine starter is calibrated to be 0.98 through a bench test, so that the output power P of the air turbine starter can be obtained when the rotating speed of the engine is 3000rpm ATS =103.08kw, from M =9549P/n, the output torque M of the air turbo starter at an engine speed of 3000rpm can be obtained st ＝9549*103.08/3000＝328.1N.m；
The fourth step: according to M General assembly ＝M st +M T And the total torque for engine start obtained by the third step is 196.6N.m, M T ＝M General assembly -M st ＝196.6-328.1＝-131.5N.m；
The fifth step: the resistance torque characteristics at different rotating speeds can be repeated in the processes from the second step to the fourth step, the N value area is 100, outliers in the outliers are removed, data fitting is carried out on the torque characteristics at different rotating speeds, and the engine starting resistance torque characteristics at different rotating speeds can be obtained.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (7)
1. A method for measuring starting resistance torque of an aircraft engine under the condition of no loading is characterized by comprising the following steps:
the method comprises the following steps that S1, a turbine starter is driven to rotate through an air source control device, a gear shaft of an accessory transmission device is driven to rotate by the turbine starter, and the turbine starter is connected with an engine transmission device through a power transmission shaft, so that the engine transmission device is driven to start, and a torque measuring device is arranged on the power transmission shaft;
s2, calibrating air source conditions in the starting process of the engine, and performing an engine starting test by using the calibrated air source conditions;
s3, acquiring the total residual torque value M measured by the torque measuring device at different rotating speeds n between the starting and the completion of the starting of the engine General (1) Recording the ambient pressure p 0 Gas source flow W a air Total pressure p t air Total temperature T t air ；
S4, determining starting resistance moment M of the aero-engine T ＝M General assembly -M st ；
Wherein, M st For turbo starter output torque:
wherein, C p Is a constant, eta Air (a) Efficiency of air pipe system, eta ATS For turbo-starter efficiency, the total pressure at the inlet of the turbo-starter is p tATS Transmission system efficiency of eta Transmission gear 。
2. The method for measuring the starting drag torque of an aircraft engine under the unloaded condition as set forth in claim 1, wherein in step S2, an engine start control plan and timing are obtained, and an engine start test is performed in accordance with the engine start control plan and timing.
3. The method for measuring the starting resistance torque of an aircraft engine under the unloaded condition as claimed in claim 2, wherein in the step S2, the air supply conditions for the calibration of the engine starting process include flow rate, temperature, pressure, parameters of the air turbine starter, parameters of the air line and the control valve, and parameters of the torque measuring device of the calibration air supply.
4. The method of measuring aircraft engine starting drag torque under unloaded conditions of claim 1, wherein said turbo starter is an air turbo starter.
5. The method of measuring aircraft engine starting drag torque under unloaded conditions of claim 1, wherein in step S4, N M are calculated T And fitting a functional relation graph of the starting resistance torque of the engine and the rotating speed of the engine.
6. Method for measuring the starting drag torque of an aircraft engine in the unloaded condition according to claim 5, characterised in that after step S4M is removed T Outlier points in the values.
7. The method for measuring the starting drag torque of an aircraft engine under the unloaded condition as claimed in claim 5, wherein in step S4, the value of N is 80 to 120.
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| CN114935419B (en) * | 2022-05-19 | 2023-09-22 | 中国航发沈阳发动机研究所 | Method for evaluating power characteristics of starter of aero-engine under installed condition |
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| US10767564B2 (en) * | 2017-03-17 | 2020-09-08 | Hamilton Sunstrand Corporation | Air turbine starter with automated variable inlet vanes |
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